Experimental investigation of transonic buffet on swept wings

A comparative study between 2D and 3D flow and analysis of sweep angle influence using stereoscopic PIV and Background Oriented Schlieren

Master thesis (2019)

Authors

C. Camps Pons Aerospace Engineering

Contributors

B.W. van Oudheusden Aerodynamics - Aerospace Engineering (mentor)
F.F.J. Schrijer Aerodynamics - Aerospace Engineering (mentor)
A. D'Aguanno Aerodynamics - Aerospace Engineering (mentor)
D.A. von Terzi Wind Energy - Aerospace Engineering (graduation committee member)
Faculty
Aerospace Engineering, Aerospace Engineering
Copyright: © 2019 Carlos Camps Pons
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Published Date

28-11-2019

Language

English

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Faculty

Aerospace Engineering

Abstract

Transonic buffet is an aerodynamic instability that appears on aerofoils and wings at certain combinations of Mach number and angle of attack, and which limits the aircraft flight envelope. This thesis project presents an experimental
investigation of buffet employing stereoscopic PIV and Background Oriented Schlieren. By using four aerodynamic models, a 2D aerofoil and three 3D wings with sweep angles of 0o, 15o and 30o, the differences between the 2D buffet typical of aerofoils and the 3D buffet typical of swept wings is studied, scrutinising the influence of the sweep angle. The results confirm that for the same aerodynamic conditions the 2D buffet experiences larger shock oscillations than the 3D case. A frequency analysis reveals a clear peak at 160 Hz for the 2D case, which is also visible in the 3D case for low sweep angles. As the sweep angle increases, this peak is replaced by a bump at higher frequencies.